Classifications

• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
  • B64G1/00—Cosmonautic vehicles
  • B64G1/002—Launch systems
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
  • B64G1/00—Cosmonautic vehicles
  • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
  • B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
  • B64G1/36—Guiding or controlling apparatus, e.g. for attitude control using sensors, e.g. sun-sensors, horizon sensors
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
  • B64G1/00—Cosmonautic vehicles
  • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
  • B64G1/40—Arrangements or adaptations of propulsion systems
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F42—AMMUNITION; BLASTING
  • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
  • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
  • F42B10/60—Steering arrangements
  • F42B10/62—Steering by movement of flight surfaces
  • F42B10/64—Steering by movement of flight surfaces of fins

Definitions

• the invention relates to a device for controlling the flight behavior of a launch vehicle, which is provided with a drive and a payload and which has at least one control and at least one steering element for changing the flight path of the launch vehicle transversely to a longitudinal axis of the launch vehicle.
• a change in the direction of movement of the launcher transversely to the longitudinal direction can take place, for example, with the aid of a thrust vector control.
• pivotally mounted drive units are provided, with the aid of which the thrust direction can be changed relative to the longitudinal axis of the rocket.
• Air / air missile it is known to use steering movements
• Rocket longitudinal axis are adjustable and provide shear forces through their respective air flow.
• the wind sensitivity thus leads to the fact that, on the one hand, the number of possible starting times is reduced, on the other hand, the structure of the rocket must be designed to be sufficiently stable in order to be able to absorb transverse forces in the permissible range. This results in an increase in the mass of the carrier rocket which, with the same drive power, results in a reduction in the maximum payload that can be absorbed.
• the object of the present invention is therefore to construct a device of the type mentioned in the introduction in such a way that the effects of wind gusts are reduced.
• the steering element is designed as a pivotably mounted guide wing which is arranged in a lateral region of the launch vehicle and in that an actuating element which is controlled by the control system in such a way that measured values provided by sensors via Side wind loads to compensate for transverse forces are implemented in positions of the guide wing, with which the guide wing is connected.
• control surfaces On the basis of these control surfaces, it is possible to actively regulate the rocket as a function of gusts currently occurring.
• the sensors create a possibility to measure the effect of the gusts on the rocket during the flight.
• the control system can specify the required deflections of the control surfaces in order to counteract the force of the gusts. This provides a gust reduction system for rockets.
• a combination of a favorable aerodynamic shape with sufficient stability for the introduction of forces into the launch vehicle is provided in that the guide wing is essentially triangular in shape and, starting from a base facing the launch vehicle, with respect to the longitudinal Axis tapers radially outwards.
• the guide wing is essentially triangular in shape and, starting from a base facing the launch vehicle, with respect to the longitudinal Axis tapers radially outwards.
• a further improvement in functionality can be achieved by providing the guide wing with a flattening in the region of its extension facing away from the launch vehicle.
• a control possibility for the compensation of wind gusts acting from different directions is provided in that four guide vanes are arranged essentially equidistantly along a circumference of the launch vehicle.
• the guide wing in a multi-stage launcher be arranged in the region of a transition from a second stage to a third stage.
• a particularly expedient arrangement in the case of a multi-stage rocket takes place in that the guide wing is arranged in the region of a transition cladding which surrounds the transition from the second stage to the third stage.
• control system be provided with two superimposed control loops.
• Exact adherence to a predetermined position of the guide vane can be achieved in that the inner circle is formed from the guide vane, the actuating element, the control and a position sensor.
• the outer circuit has sensors for detecting the influence of the cross winds, a control for reducing the gust, and a setpoint generator.
• the device for controlling the flight behavior of a launch vehicle (1) essentially consists of guide wings (2) which are arranged in a lateral region (3) of the launch vehicle (1).
• the launch vehicle (1) is formed from a first stage (4), a second stage (5), a third stage (6) and a payload (15).
• a transition from the second stage (5) to the third stage (6) is provided with a transition cladding (7) and in the area of this transition cladding (7) four guide vanes (2) are arranged which are uniform over the circumference of the transition Covering (7) are distributed and thereby each angle between them of about 90 °.
• the guide vanes (2) have an approximately triangular contour. Starting from a base arranged facing the launcher (1), the guide vanes (2) taper in an outward direction. In particular, it is contemplated that a region of the guide vanes (2) facing away from the launch vehicle (1) be provided with a flattened portion (8). A boundary of the guide vanes (2) facing the first stage (4) extends essentially perpendicular to a longitudinal axis (9) of the carrier rocket (1). A boundary facing the third stage runs obliquely to the longitudinal axis (9) and is passed in the region of its end facing away from the launch vehicle (1) through the flattening (8) into the boundary facing the first stage (4).
• the guide vanes (2) which are connected to the launcher (1) can be pivoted. aligned such that guide surfaces (10) are aligned with respect to one in the direction of the longitudinal axis (9)
• the circuitry combination of the essential functional components is shown in FIG. 2.
• the guide wing (2) is connected to an actuating element (11), the function of which is controlled by a controller (12).
• the controller (12) evaluates measurement signals from sensors (13) for the detection of side wind influences on the launch vehicle (1).
• a position sensor (14) is arranged in the area of the guide vane (2), which is also connected to the controller (12). Additional sensors can also be used to set up a complex control system.
• control (12) is in particular equipped with two superimposed control loops.
• the inner control loop consists of the guide vane (2), the control element (11), the control (12) and the position sensor (14). This control loop is used to control the position of the guide vanes (2).
• the outer control loop supplements the inner control loop by the sensors (13) for the detection of the side wind influence, a control (18) for gust reduction and a setpoint generator (16).
• the two control loops act on the rocket (1), which is influenced by gusts (17).

Landscapes

• Engineering & Computer Science (AREA)
• Remote Sensing (AREA)
• Aviation & Aerospace Engineering (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Physics & Mathematics (AREA)
• Radar, Positioning & Navigation (AREA)
• Fluid Mechanics (AREA)
• General Engineering & Computer Science (AREA)
• Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
• Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
• Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
• Transmission Devices (AREA)

Priority Applications (3)

Applications Claiming Priority (2)

Publications (1)

Family

ID=6478151

Family Applications (1)

Country Status (7)

Cited By (1)

Families Citing this family (15)

Citations (6)

Family Cites Families (10)

• 1993
  • 1993-01-14 DE DE4300761A patent/DE4300761A1/de not_active Withdrawn
• 1994
  • 1994-01-13 EP EP94904571A patent/EP0632879A1/de not_active Withdrawn
  • 1994-01-13 JP JP6515590A patent/JPH07507521A/ja active Pending
  • 1994-01-13 RU RU94042469/02A patent/RU94042469A/ru unknown
  • 1994-01-13 WO PCT/DE1994/000025 patent/WO1994016286A1/de not_active Application Discontinuation
  • 1994-01-13 US US08/302,809 patent/US5593110A/en not_active Expired - Fee Related
  • 1994-01-14 CN CN94101924A patent/CN1107114A/zh active Pending

Patent Citations (6)

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